Unmanned aerial vehicle pitot tube connecting structure

Abstract

The utility model relates to a unmanned aerial vehicle airspeed tube connecting structure belongs to unmanned aerial vehicle body structure field, including airspeed tube, main joint, vice joint and reinforcing gusset, wherein main joint and vice joint are all the integral connection constitution of bottom plate and pipe column, the bottom plate of main joint is fixed on the inside reinforcing frame of nose, vice joint sets up in the outside of nose skin and with main joint along airspeed tube axial interval distribution, the bottom plate of vice joint is installed in the outside of nose skin, the fixed end of airspeed tube is in proper order and penetrates vice joint, nose skin, reinforcing gusset and main joint, three are through fastening assembly and form coaxial rigid connection, reinforcing gusset is opened and has the inner hole of penetrating airspeed tube, is embedded in the inside of nose skin, and is connected through bolt, nut assembly with the vice joint bottom plate of being located in the outside of nose skin.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) airframe structure, specifically relating to a UAV airspeed tube connection structure. Background Technology

[0002] The airspeed sensor of a drone is partially mounted in front of the wing and partially in front of the nose. To ensure accuracy, the airspeed sensor needs to be kept at a distance from the fuselage structure. Generally, a long tubular structure extends out of the fuselage as a base to mount the airspeed sensor. The structure extending out of the fuselage needs to have sufficient rigidity to ensure that it will not deform significantly under aerodynamic forces, thus affecting the speed measurement.

[0003] Currently, the pitot tube installation on the nose of unmanned aerial vehicles (UAVs) generally adopts a dual-joint support scheme: both the main and auxiliary joints are located inside the nose compartment, and the pitot tube is fixed by a cantilever structure. This method has two inherent drawbacks:

[0004] 1. Insufficient support stiffness: Due to space constraints at the nose, the distance between the two joints is small, resulting in low bending stiffness at the cantilever end. Under aerodynamic loads, it is prone to deformation, affecting the measurement accuracy of the airspeed sensor.

[0005] 2. The conflict between disassembly / reassembly efficiency and structural design: To meet the length restrictions for relocation and transportation, the pitot tube needs to be frequently disassembled. However, traditional structures are complex to disassemble (requiring the separation of all joints), and it is difficult to guarantee the initial stiffness after reinstallation. Simplifying the connection for easier disassembly / reassembly would further sacrifice the reliability of the support structure.

[0006] Therefore, there is an urgent need for a pitot tube connection solution that can simultaneously improve support stiffness and disassembly / reassembly efficiency. Summary of the Invention

[0007] The technical problem to be solved:

[0008] To overcome the shortcomings of existing technologies, this invention provides a pitot tube connection structure for unmanned aerial vehicles (UAVs). It overcomes the spatial limitations of the nose section through spatial reconfiguration (outward relocation of the sub-connector) and systematically solves the problem using modular pre-assembly (sub-connector + pitot tube) and localized reinforcement design (reinforcing pad). This invention resolves the conflict between nose section space constraints and cantilever stiffness requirements, enabling simultaneous and rapid assembly and disassembly of the pitot tube and sub-connector while ensuring a high-rigidity connection, thus adapting to relocation and transportation requirements.

[0009] The technical solution of this utility model is: a pitot tube connection structure for unmanned aerial vehicles, including a pitot tube 2, a main connector 3, a secondary connector 5 and a reinforcing pad 4, wherein the main connector 3 and the secondary connector 5 are integrally connected to the base plate and the tube column;

[0010] The base plate of the main connector 3 is fixed to the internal reinforcing frame of the machine head;

[0011] The auxiliary connector 5 is located on the outside of the nose skin and is spaced apart from the main connector 3 along the axial direction of the airspeed tube; the base plate of the auxiliary connector 5 is installed on the outside of the nose skin.

[0012] The fixed end of the airspeed tube 2 passes through the auxiliary connector 5, the nose skin, the reinforcing pad 4 and the main connector 3 in sequence, and the three are connected in a coaxial rigid connection by fastening components;

[0013] The reinforcing pad 4 has an inner hole that penetrates the pitot tube 2, is embedded in the inner side of the nose skin, and is connected to the base plate of the auxiliary connector 5 located on the outer side of the nose skin by bolts and nuts.

[0014] A further technical solution of this utility model is: the bottom plate profile of the main connector 3 is consistent with the internal reinforcing frame profile of the machine head, and is fixedly installed by 4 sets of high-strength bolts and high-strength nuts.

[0015] A further technical solution of this utility model is: the bottom plate of the sub-connector 5 is consistent with the outer surface of the machine head skin, and is fixedly installed to the reinforcing pad 4 on the inner side of the machine head skin by 4 sets of bolt and nut assemblies.

[0016] A further technical solution of this utility model is: the auxiliary connector 5 and the airspeed tube 2 are pre-installed as a detachable module, and when disassembling the airspeed tube 2, it is only necessary to separate the fasteners on the base plate of the auxiliary connector 5 and the fasteners between the main connector 3 and the airspeed tube 2.

[0017] A further technical solution of this utility model is: the outer diameter of the fixed end of the airspeed tube 2 is smaller than the outer diameter of the cantilever end, and a step difference of 0.5mm is formed between the two by radial milling.

[0018] A further technical solution of this utility model is that the fixed end of the airspeed tube 2, the tube end of the auxiliary connector 5, the inner hole of the reinforcing pad 4, and the tube end of the main connector 3 are all clearance fit.

[0019] A further technical solution of this utility model is: the main connector 3 has two sets of first fastening holes at the end of the tube, and the auxiliary connector 5 has two sets of second fastening holes at the end of the tube.

[0020] The axes of the first and second fastening holes are perpendicular to each other and bear lateral and vertical aerodynamic loads, respectively.

[0021] A further technical solution of this utility model is: fastening components are installed in both the first fastening hole and the second fastening hole to connect the airspeed tube 2 to the main connector 3 and the auxiliary connector 5 respectively. The fastening components include bolts, nuts and washers.

[0022] A further technical solution of this utility model is: the reinforcing pad 4 is a square aluminum alloy plate, the area of ​​which is larger than the area of ​​the base plate of the sub-joint 5, so as to distribute the load of the composite skin; the four corners of the reinforcing pad 4 are provided with mounting holes for the support plate nut.

[0023] A further technical solution of this utility model is: the four mounting holes on the base plate of the sub-connector 5 are arranged opposite to the four mounting holes of the reinforcing pad 4.

[0024] Beneficial effects

[0025] The beneficial effects of this utility model are as follows: This utility model solves the problem that the small spacing between the main and auxiliary connector fixing points inside the cabin of the pitot tube, which is installed directly in front of the nose, makes it difficult to provide sufficient support rigidity for the cantilever end of the pitot tube. It also addresses the issue that the pitot tube and auxiliary connector need to be removed simultaneously during UAV relocation and transportation. Specific advantages are analyzed as follows:

[0026] 1. Significantly improves support stiffness, ensuring speed measurement accuracy.

[0027] This invention moves the auxiliary joint 5 to the outside of the nose skin, forming a cross-cabin double-support structure with the main joint 3 inside the cabin. Finite element analysis shows that the deformation of the cantilever end under aerodynamic loads is reduced, fundamentally solving the problem of airspeed measurement error caused by insufficient stiffness.

[0028] 2. Achieving both rapid assembly / disassembly and high reliability.

[0029] The auxiliary connector 5 and the airspeed tube 2 of this utility model are pre-assembled as an integral module. When disassembling, only 6 sets of fasteners (2 sets of main connectors + 4 sets of auxiliary connector base plates) need to be separated, and the disassembly and assembly time is reduced to 1 / 3 of that of the traditional structure. The orthogonally arranged fasteners resist the lateral / vertical loads respectively. After reinstallation, the connection stiffness attenuation rate is reduced, avoiding performance degradation caused by repeated disassembly and assembly.

[0030] 3. The reinforcing pad 4 of this utility model distributes the load of the sub-joint through the support plate nut, thereby improving the service life of the composite skin.

[0031] 4. The form adopted by this utility model provides reliable support rigidity, reliable connection, and convenient and quick assembly and disassembly. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the installation of a UAV pitot tube connection structure in an embodiment of this utility model;

[0033] Figure 2 This is a cross-sectional schematic diagram of a UAV pitot tube connection structure in an embodiment of this utility model;

[0034] Figure 3 This is a schematic diagram of the airspeed tube structure in an embodiment of this utility model;

[0035] Figure 4 This is a schematic diagram of the main connector structure in an embodiment of this utility model;

[0036] Figure 5This is a schematic diagram of the reinforcing pad structure in an embodiment of this utility model;

[0037] Figure 6 This is a schematic diagram of the sub-connector structure in an embodiment of this utility model.

[0038] Explanation of reference numerals in the attached drawings: 1. UAV airspeed tube connection structure; 2. Airspeed tube; 21. Cantilever end; 22. Fixed end; 23. Cable hole; 3. Main connector; 4. Reinforcing pad; 5. Sub-connector; 6. Bolt support plate and nut assembly; 7. Bolt, nut, and washer assembly; 8. Airspeed sensor; 9. Skin; 10. Reinforcing frame. Detailed Implementation

[0039] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0040] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0041] Based on the shortcomings of the current dual-joint support scheme commonly used for pitot tube installation on UAV nose sections, this utility model proposes a UAV pitot tube connection structure, including a pitot tube 2, a main connector 3, a secondary connector 5, and a reinforcing pad 4. The main connector 3 and the secondary connector 5 are both integrally connected as a base plate and a tube column. The base plate of the main connector 3 is fixed to the internal reinforcing frame of the nose section. The secondary connector 5 is located on the outer side of the nose skin and is spaced apart from the main connector 3 along the pitot tube axis. The base plate of the secondary connector 5 is installed on the outer side of the nose skin. The fixed end of the pitot tube 2 sequentially passes through the secondary connector 5, the nose skin, the reinforcing pad 4, and the main connector 3, forming a coaxial rigid connection through a fastening assembly. The reinforcing pad 4 has an inner hole penetrating the pitot tube 2, is embedded inside the nose skin, and is connected to the base plate of the secondary connector 5 located on the outer side of the nose skin via bolts and nuts.

[0042] In one embodiment, the base plate profile of the main connector 3 is consistent with the internal reinforcing frame profile of the machine head, and is fixedly installed by four sets of high-strength bolts and high-strength nuts.

[0043] In one embodiment, the base plate of the sub-connector 5 is consistent with the outer surface of the head skin, and is fixedly installed to the reinforcing pad 4 on the inner side of the head skin by four sets of bolt and nut assemblies (i.e., bolt support plate and nut assembly 6).

[0044] In one embodiment, the auxiliary connector 5 and the airspeed tube 2 are pre-installed as a detachable module. When disassembling the airspeed tube 2, it is only necessary to separate the fasteners on the base plate of the auxiliary connector 5 and the fasteners between the main connector 3 and the airspeed tube 2.

[0045] In one embodiment, the outer diameter of the fixed end of the airspeed tube 2 is smaller than the outer diameter of the cantilever end, and a step difference of 0.5 mm is formed between the two by radial milling.

[0046] In one embodiment, the fixed end of the airspeed tube 2, the tube end of the auxiliary connector 5, the inner hole of the reinforcing pad 4, and the tube end of the main connector 3 are all clearance fit.

[0047] In one embodiment, the main connector 3 has two sets of first fastening holes at the end of the tubing, and the auxiliary connector 5 has two sets of second fastening holes at the end of the tubing.

[0048] The axes of the first and second fastening holes are perpendicular to each other and bear lateral and vertical aerodynamic loads, respectively.

[0049] In one embodiment, fastening components are installed in both the first and second fastening holes to connect the airspeed tube 2 to the main connector 3 and the auxiliary connector 5 respectively. The fastening components (i.e., the bolt, nut and washer assembly 7) include bolts, nuts and washers.

[0050] In one embodiment, the reinforcing pad 4 is a square aluminum alloy plate with an area larger than that of the base plate of the sub-joint 5, so as to distribute the load of the composite skin; the four corners of the reinforcing pad 4 are provided with mounting holes for the support plate nut.

[0051] In one embodiment, the four mounting holes on the base plate of the sub-connector 5 are arranged opposite to the four mounting holes on the reinforcing pad 4.

[0052] The above technical solution will be further explained below with reference to the accompanying drawings:

[0053] In one embodiment, refer to Figure 1 , Figure 2 As shown, an airspeed tube connection structure 1 for UAVs is used to install an airspeed sensor located at the front of the nose, and consists of an airspeed tube 2, a main connector 3, a reinforcing pad 4, and a secondary connector 5.

[0054] In one embodiment, refer to Figure 3As shown, the airspeed tube 2 includes a cantilever end and a fixed end, and is made of finished aluminum alloy tubing. The outer diameter of the cantilever end is not machined, and the outer diameter of the fixed end is milled inward by 0.5mm. The reduced outer diameter facilitates disassembly and installation. The airspeed sensor is inserted at the front of the cantilever end and connected by screws. The fixed end of the airspeed tube 2 is provided with a wire through hole.

[0055] Reference Figure 4-6 As shown, the main connector 3, the reinforcing pad 4, and the auxiliary connector 5 are all made of machined aluminum alloy.

[0056] During installation, first connect main connector 3 (e.g. Figure 4 The machine is installed on the reinforcing frame using a non-removable assembly of four sets of high-strength bolts and nuts. Then, four reinforcing pads (such as...) are installed inside the head skin. Figure 5 ), using 4 sets of support plate nuts for connection, and connecting the auxiliary connector 5 (such as Figure 6 Insert the airspeed sensor into the fixed end of the airspeed tube 2, then insert the fixed reinforcing pad 4 and main connector 3; the outer surface of the fixed end of the airspeed tube 2 is fitted with a small clearance to the inner surface of the tube end of the reinforcing pad 4, main connector 3, and auxiliary connector 5; insert two sets of bolts, nuts, and washers into the outer surface of the tube end of the main connector 3 and connect them to the end of the fixed end of the airspeed tube 2; attach the base plate of the auxiliary connector 5 to the skin and reinforcing pad 4, and use four bolts to engage with the already connected support plate nut. The reinforcing pad 4 serves as a local reinforcement structure for the composite skin of the engine head, preventing frequent disassembly from damaging the composite skin structure; then insert two sets of bolts, nuts, and washers into the outer surface of the tube end of the auxiliary connector 5 and fix it to the airspeed tube 2; the main connector 3 (such as...) Figure 4 ), Sub-connector 5 (such as Figure 6 The fastener connection holes on the device are oriented vertically to facilitate the bearing of vertical and horizontal loads and ensure sufficient support rigidity.

[0057] During disassembly, the two sets of fasteners between the auxiliary connector 5 and the airspeed tube 2 do not need to be removed. Remove the four bolts that connect the base plate of the auxiliary connector 5 to the skin and reinforcing pad 4, and remove the two sets of bolts, nuts, and washers that connect the airspeed tube 2 and the main connector 3, thus removing the airspeed tube.

[0058] In one embodiment, the steps for disassembling and maintaining the pitot tube connection structure include:

[0059] Step 1: Disconnect the two sets of fasteners connecting the airspeed tube 2 and the main connector 3;

[0060] Step 2: Disconnect the four sets of bolts connecting the auxiliary connector 5 on the airspeed tube 2 to the skin and reinforcing pad 4;

[0061] Step 3: Pull the airspeed tube forward, loosen the connecting screw between the airspeed sensor and airspeed tube 2, and remove the airspeed sensor.

[0062] The process of restoring the above steps includes:

[0063] Step 1: Install the airspeed sensor on airspeed tube 2;

[0064] Step 2: Insert the installed airspeed tube into the auxiliary connector 5 and the main connector 3;

[0065] Step 3: Install the two sets of fasteners connecting the airspeed tube 2 and the main connector 3;

[0066] Step 4: Install the four sets of bolts connecting the auxiliary connector 5 on the airspeed tube 2 to the skin and reinforcing pad 4.

[0067] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A pitot tube connection structure for a UAV, characterized in that: It includes an airspeed tube (2), a main connector (3), a secondary connector (5) and a reinforcing pad (4), wherein the main connector (3) and the secondary connector (5) are both integrally connected to the base plate and the tube string; The base plate of the main connector (3) is fixed to the internal reinforcing frame of the machine head; The auxiliary connector (5) is located on the outside of the nose skin and is spaced apart from the main connector (3) along the axial direction of the airspeed tube; the base plate of the auxiliary connector (5) is installed on the outside of the nose skin; The fixed end of the airspeed tube (2) passes through the auxiliary connector (5), the nose skin, the reinforcing pad (4) and the main connector (3) in sequence, and the three are connected in a coaxial rigid connection by fastening components; The reinforcing pad (4) has an inner hole that penetrates the airspeed tube (2), is fitted inside the nose skin, and is connected to the base plate of the auxiliary connector (5) located on the outside of the nose skin by bolts and nuts.

2. The UAV pitot tube connection structure according to claim 1, characterized in that: The bottom plate of the main connector (3) is consistent with the internal reinforcing frame of the machine head and is fixedly installed by four sets of high-strength bolts and high-strength nuts.

3. The UAV pitot tube connection structure according to claim 1, characterized in that: The bottom plate of the sub-joint (5) is consistent with the outer surface of the head skin, and is fixedly installed to the reinforcing pad (4) on the inner side of the head skin by four sets of bolts and nuts.

4. The UAV pitot tube connection structure according to claim 1, characterized in that: The sub-connector (5) and the airspeed tube (2) are pre-installed as a detachable module. When disassembling the airspeed tube (2), it is only necessary to separate the fasteners on the base plate of the sub-connector (5) and the fasteners between the main connector (3) and the airspeed tube (2).

5. The UAV pitot tube connection structure according to claim 1, characterized in that: The outer diameter of the fixed end of the airspeed tube (2) is smaller than the outer diameter of the cantilever end, and a step difference of 0.5 mm is formed between the two by radial milling.

6. The UAV pitot tube connection structure according to claim 1, characterized in that: The fixed end of the airspeed tube (2), the tube end of the auxiliary connector (5), the inner hole of the reinforcing pad (4), and the tube end of the main connector (3) are all clearance fit.

7. The UAV pitot tube connection structure according to claim 1, characterized in that: The main connector (3) has two sets of first fastening holes at the pipe end, and the auxiliary connector (5) has two sets of second fastening holes at the pipe end. The axes of the first and second fastening holes are perpendicular to each other and bear lateral and vertical aerodynamic loads, respectively.

8. The UAV pitot tube connection structure according to claim 7, characterized in that: Both the first and second fastening holes are fitted with fastening components to connect the airspeed tube (2) to the main connector (3) and the auxiliary connector (5) respectively. The fastening components include bolts, nuts and washers.

9. The UAV pitot tube connection structure according to claim 1, characterized in that: The reinforcing pad (4) is a square aluminum alloy plate with an area larger than that of the base plate of the sub-joint (5) to distribute the load of the composite skin; the four corners of the reinforcing pad (4) are provided with mounting holes for the support plate nut.

10. The UAV pitot tube connection structure according to claim 9, characterized in that: The four mounting holes on the base plate of the sub-connector (5) are arranged opposite to the four mounting holes of the reinforcing pad (4).

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